General Electric Company

Daniel Robert Tegel

Geoffrey David Myers

Abdul-Azeez Mohammed-Fakir

Keith Cletus Belsom

David August Snider

Joseph Vincent Citeno

Charles E Steber

James Harper

Calvin Levy Sims

Scott Alan Kopcho

Stephen R Watts

Henry Joe Wiersma

Siddharth Aphale

Aarron Dell Johansen

Eric Motter

Gerald P Hunt

Robert Edward Malo

Jack Edward Lawton

Methods of determining a desired sensor probe location in a closed loop emissions control (CLEC) system of a gas turbine engine are provided. One method includes determining, at different locations, a plurality of temperature contour profiles for exhaust flowing through an exhaust duct, selecting an emissions component entrained in the exhaust to be measured, and determining a desired sensor probe installation location based on the emissions component to be measured and based on the plurality of temperature contour profiles.

Methods of determining sensor probe location in a closed loop emissions control system

Methods and systems for delivering fuel in a gas turbine engine are provided. The system includes a plurality of can annular combustors that includes at least a first set of combustors of the plurality of can annular combustors and at least a second set of combustors of the plurality of can annular combustors wherein each set of combustors is supplied by a separately controllable respective fuel delivery system. The method includes supplying fuel at a first fuel schedule to the first set of combustors and supplying fuel at a second fuel schedule to the second set of combustors during a first mode of operation wherein the second fuel schedule is different than the first fuel schedule, and supplying fuel at the second fuel schedule to the first and second sets of combustors during a second mode of operation.

Methods and systems for operating gas turbine engines

A method of detecting combustor dynamic pressures in combustors of a gas turbine combustor includes the steps of: a) mounting at least one accelerometer ( ) on a combustor casing; b) establishing a baseline vibration signature for the casing when combustion dynamics are minimal; and c) measuring subsequent vibration signatures and comparing those signatures to the baseline signature.

Measurement method for detecting and quantifying combustor dynamic pressures

In a combustor having an axis, a flow sleeve and a liner, a plurality of circumferentially spaced supports interconnect the upstream ends of the liner and flow sleeve to limit wear on the supports and accommodate relative thermal expansion of the liner and flow sleeve. Each support includes a flow sleeve stop having an angled surface, a groove and a female threaded aperture and a liner stop having a complementary angled surface, a rib and an enlarged opening. By inserting the liner axially through the open upstream end of the flow sleeve, the rib of the liner stop engages the slot of the flow sleeve stop. By passing a bolt having a spring through the enlarged opening of the liner stop and threading the bolt to the flow sleeve stop, the liner is biased for axial downstream movement to maintain the complementary inclined surfaces of the stops in contact with one another, thereby limiting wear and accommodating relative thermal expansion of the flow sleeve and liner.

Supports for connecting a flow sleeve and a liner in a gas turbine combustor

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Simpsonville, SC, United States of America

Daniel Robert Tegel